NREL's S816 Airfoil (s816-nr) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: NREL's S816 Airfoil (s816-nr) Reynolds number: 200,000 Max Cl/Cd: 60.57 at α=7.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s816-nr-200000-n5.txt Download as CSV file: xf-s816-nr-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NREL's S816 Airfoil
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.750 -0.4299 0.10497 0.10140 -0.0711 1.0000 0.0092
-13.500 -0.4505 0.09857 0.09497 -0.0733 1.0000 0.0090
-13.250 -0.4724 0.09175 0.08806 -0.0763 0.9972 0.0091
-13.000 -0.4896 0.08494 0.08112 -0.0802 0.9887 0.0089
-12.750 -0.5050 0.07851 0.07451 -0.0840 0.9804 0.0085
-12.500 -0.5209 0.07231 0.06811 -0.0870 0.9685 0.0084
-12.250 -0.5305 0.06719 0.06277 -0.0894 0.9486 0.0084
-12.000 -0.5357 0.06145 0.05673 -0.0922 0.9160 0.0083
-11.750 -0.5276 0.05632 0.05122 -0.0963 0.8790 0.0085
-11.500 -0.5199 0.05056 0.04493 -0.0974 0.8478 0.0083
-11.250 -0.5124 0.04836 0.04243 -0.0977 0.8189 0.0088
-11.000 -0.5003 0.04553 0.03924 -0.0971 0.7993 0.0092
-10.750 -0.4759 0.04236 0.03561 -0.0963 0.7846 0.0097
-10.500 -0.4284 0.03990 0.03247 -0.0952 0.7732 0.0105
-10.250 -0.3958 0.03915 0.03150 -0.0943 0.7612 0.0108
-10.000 -0.3683 0.03872 0.03092 -0.0935 0.7503 0.0111
-9.750 -0.3434 0.03841 0.03049 -0.0926 0.7407 0.0117
-9.250 -0.2935 0.03846 0.03025 -0.0899 0.7243 0.0132
-9.000 -0.2744 0.03827 0.02994 -0.0887 0.7174 0.0137
-8.750 -0.2593 0.03781 0.02947 -0.0875 0.7107 0.0151
-8.500 -0.2451 0.03722 0.02884 -0.0866 0.7047 0.0163
-8.250 -0.2312 0.03661 0.02814 -0.0856 0.6994 0.0189
-8.000 -0.2202 0.03585 0.02738 -0.0845 0.6938 0.0206
-7.750 -0.2101 0.03502 0.02649 -0.0834 0.6892 0.0221
-7.500 -0.2031 0.03400 0.02543 -0.0822 0.6851 0.0253
-7.250 -0.1965 0.03287 0.02429 -0.0811 0.6809 0.0283
-7.000 -0.1922 0.03162 0.02299 -0.0798 0.6771 0.0312
-6.750 -0.1912 0.03022 0.02158 -0.0783 0.6737 0.0345
-6.500 -0.1895 0.02879 0.02006 -0.0768 0.6708 0.0385
-6.250 -0.1937 0.02689 0.01815 -0.0751 0.6674 0.0421
-6.000 -0.1974 0.02500 0.01621 -0.0735 0.6642 0.0465
-5.750 -0.2018 0.02311 0.01422 -0.0717 0.6612 0.0510
-5.500 -0.2117 0.02126 0.01229 -0.0691 0.6585 0.0559
-5.250 -0.2160 0.02000 0.01089 -0.0666 0.6562 0.0633
-5.000 -0.2102 0.01902 0.00985 -0.0650 0.6536 0.0781
-4.750 -0.2000 0.01812 0.00893 -0.0638 0.6510 0.1045
-4.500 -0.2097 0.01541 0.00690 -0.0612 0.6485 0.3351
-4.250 -0.1877 0.01522 0.00690 -0.0610 0.6461 0.4335
-4.000 -0.1608 0.01539 0.00699 -0.0613 0.6439 0.4527
-3.750 -0.1334 0.01560 0.00705 -0.0616 0.6419 0.4655
-3.500 -0.1053 0.01586 0.00727 -0.0619 0.6401 0.4737
-3.250 -0.0782 0.01589 0.00714 -0.0623 0.6382 0.4793
-3.000 -0.0503 0.01605 0.00732 -0.0625 0.6362 0.4833
-2.750 -0.0225 0.01615 0.00739 -0.0628 0.6344 0.4873
-2.500 0.0051 0.01613 0.00727 -0.0633 0.6326 0.4901
-2.250 0.0329 0.01605 0.00709 -0.0638 0.6310 0.4915
-2.000 0.0608 0.01598 0.00691 -0.0643 0.6295 0.4927
-1.750 0.0890 0.01592 0.00675 -0.0649 0.6281 0.4939
-1.500 0.1172 0.01588 0.00668 -0.0654 0.6269 0.4948
-1.250 0.1457 0.01587 0.00663 -0.0660 0.6257 0.4958
-1.000 0.1734 0.01586 0.00662 -0.0664 0.6244 0.4969
-0.750 0.2008 0.01586 0.00663 -0.0668 0.6228 0.4981
-0.500 0.2283 0.01587 0.00665 -0.0673 0.6211 0.4994
-0.250 0.2559 0.01588 0.00666 -0.0677 0.6195 0.5008
0.000 0.2837 0.01590 0.00667 -0.0682 0.6180 0.5023
0.250 0.3116 0.01593 0.00670 -0.0687 0.6168 0.5040
0.500 0.3396 0.01596 0.00672 -0.0692 0.6156 0.5057
0.750 0.3678 0.01600 0.00674 -0.0698 0.6145 0.5076
1.000 0.3961 0.01605 0.00678 -0.0704 0.6134 0.5092
1.250 0.4242 0.01610 0.00689 -0.0709 0.6124 0.5106
1.500 0.4525 0.01618 0.00700 -0.0714 0.6115 0.5122
1.750 0.4811 0.01627 0.00712 -0.0720 0.6106 0.5139
2.000 0.5082 0.01638 0.00731 -0.0724 0.6095 0.5158
2.250 0.5344 0.01650 0.00750 -0.0726 0.6080 0.5179
2.500 0.5608 0.01662 0.00769 -0.0729 0.6065 0.5201
2.750 0.5876 0.01675 0.00788 -0.0732 0.6052 0.5224
3.000 0.6143 0.01690 0.00811 -0.0736 0.6040 0.5244
3.250 0.6409 0.01704 0.00837 -0.0738 0.6028 0.5263
3.500 0.6676 0.01721 0.00864 -0.0741 0.6017 0.5286
3.750 0.6946 0.01737 0.00890 -0.0745 0.6005 0.5311
4.000 0.7219 0.01752 0.00913 -0.0749 0.5992 0.5339
4.250 0.7496 0.01768 0.00936 -0.0754 0.5981 0.5368
4.500 0.7773 0.01785 0.00963 -0.0759 0.5972 0.5394
4.750 0.8054 0.01801 0.00991 -0.0764 0.5961 0.5417
5.000 0.8322 0.01821 0.01023 -0.0767 0.5948 0.5442
5.250 0.8535 0.01851 0.01072 -0.0761 0.5924 0.5469
5.500 0.8763 0.01879 0.01115 -0.0757 0.5901 0.5499
5.750 0.9006 0.01904 0.01153 -0.0756 0.5880 0.5530
6.000 0.9262 0.01918 0.01183 -0.0757 0.5856 0.5556
6.250 0.9622 0.01872 0.01138 -0.0770 0.5804 0.5586
6.500 0.9784 0.01842 0.01124 -0.0750 0.5690 0.5618
6.750 0.9987 0.01797 0.01085 -0.0735 0.5561 0.5654
7.000 1.0178 0.01769 0.01066 -0.0719 0.5439 0.5692
7.250 1.0375 0.01750 0.01060 -0.0705 0.5331 0.5723
7.500 1.0535 0.01749 0.01073 -0.0686 0.5216 0.5758
7.750 1.0655 0.01759 0.01100 -0.0661 0.5077 0.5795
8.000 1.0728 0.01772 0.01125 -0.0627 0.4894 0.5833
8.250 1.0762 0.01780 0.01131 -0.0585 0.4461 0.5864
8.500 1.0603 0.01867 0.01176 -0.0516 0.3835 0.5892
8.750 1.0383 0.02043 0.01324 -0.0450 0.3343 0.5923
9.000 1.0179 0.02260 0.01521 -0.0397 0.2921 0.5955
9.250 0.9991 0.02512 0.01753 -0.0354 0.2525 0.5989
9.500 0.9832 0.02781 0.02007 -0.0321 0.2156 0.6018
9.750 0.9717 0.03042 0.02256 -0.0295 0.1812 0.6052
10.000 0.9638 0.03293 0.02493 -0.0275 0.1506 0.6089
10.250 0.9605 0.03520 0.02709 -0.0259 0.1264 0.6132
10.500 0.9600 0.03730 0.02914 -0.0245 0.1060 0.6170
10.750 0.9625 0.03923 0.03105 -0.0235 0.0913 0.6212
11.000 0.9670 0.04106 0.03288 -0.0226 0.0793 0.6261
11.250 0.9730 0.04281 0.03466 -0.0219 0.0700 0.6310
11.500 0.9786 0.04463 0.03654 -0.0212 0.0621 0.6359
11.750 0.9856 0.04638 0.03833 -0.0206 0.0551 0.6415
12.000 0.9929 0.04816 0.04019 -0.0202 0.0499 0.6473
12.250 1.0006 0.04992 0.04203 -0.0197 0.0452 0.6530
12.500 1.0068 0.05187 0.04401 -0.0193 0.0413 0.6594
12.750 1.0158 0.05357 0.04585 -0.0190 0.0380 0.6654
13.000 1.0228 0.05551 0.04786 -0.0187 0.0348 0.6721
13.250 1.0294 0.05754 0.04997 -0.0185 0.0322 0.6788
13.500 1.0381 0.05937 0.05196 -0.0183 0.0297 0.6864
13.750 1.0460 0.06133 0.05401 -0.0182 0.0276 0.6943
14.000 1.0501 0.06375 0.05649 -0.0181 0.0258 0.7022
14.250 1.0592 0.06565 0.05855 -0.0181 0.0241 0.7110
14.500 1.0675 0.06768 0.06072 -0.0182 0.0222 0.7205
14.750 1.0740 0.06991 0.06307 -0.0183 0.0209 0.7299
15.000 1.0774 0.07255 0.06577 -0.0184 0.0196 0.7394
15.250 1.0854 0.07469 0.06811 -0.0185 0.0184 0.7509
15.500 1.0921 0.07699 0.07057 -0.0187 0.0170 0.7634
15.750 1.0974 0.07949 0.07322 -0.0190 0.0159 0.7774
16.000 1.1000 0.08231 0.07616 -0.0194 0.0151 0.7932
16.500 1.1069 0.08754 0.08182 -0.0195 0.0132 0.8384
16.750 1.1064 0.08995 0.08448 -0.0189 0.0124 0.8956
17.000 1.1058 0.09273 0.08739 -0.0194 0.0118 1.0000
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